A Study on Model of Strapdown Inertial/Starlight Integrated Guidance System for Ballistic Missiles
WANG Xin-long,XIE Jia,GUO Long-hua(School of Astronautics,Beijing University of Aeronautics and Astronautics,Beijing 100083,China)
The principle of using the measurement information of starlight guidance system to adjust the errors of pose angles of strapdown inertial guidance was deduced.The major errors of intergrated guidance system were discussed,and the error model of strapdown inertial/starlight integrated guidance system was founded.Aiming at the guidance errors caused by the errors of initial position,attitude alignment and inertia sensors,a novel scheme was proposed to use the starlight guidance to update the strapdown inertial guidance system.The simulation results show that the plan of using the precise pose measurement value of stellar-trackers to adjust the strapdown inertial guidance system is reasonable and feasible,and the characteristics of this independent integrated guidance system can satisfy high precise guidance demand of ballistic missiles.
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